Nacelle equipped with a device for detecting the locking state of a locking device

Abstract

A nacelle includes a front air inlet section, a mid-section and a rear section formed from two half-shells connected each other by a locking device actuated by a control handle equipped with a secondary locking system. The secondary locking system includes a blocking member to block the control handle in a locking position. In particular, the blocking member has a rod accommodated in the control handle and prolonged by a head. The blocking member and a region of the internal face of one of two cowls of the middle section come into abutment one against the other in order to prevent the closure of cowl if the control handle is not situated in its locking position.

The invention claimed is: 
     
       1. A turbojet engine nacelle comprising:
 a front air inlet section, 
 a middle section surrounding a blower of the turbojet engine, and 
 a rear section formed from at least two half-shells connected to one another by means of at least one locking device actuated by a control handle equipped with a secondary locking system comprising a blocking member that, once placed in a blocking position, blocks said control handle in a locking position, said middle section being formed from at least two shrouds that deploy between an operating position and a maintenance position, 
 wherein the blocking member comprises a rod parallel to the control handle and slidably housed within the control handle, the control handle being linearly prolonged by a head of the rod, the blocking member and at least one zone of an internal face of one of the two shrouds abutting one against another in order to prevent the closing of said shroud if the control handle is not located in the locking position and/or if the blocking member is not in the blocking position, and 
 wherein the control handle is displaced by rotation alternately between a stable opening position in which said at least one locking device is open and a stable locking position in which said at least one locking device is closed, passing through an intermediate phase where said at least one locking device is closed. 
 
     
     
       2. The nacelle as claimed in  claim 1 , wherein the head comprises at least one protuberance. 
     
     
       3. The nacelle as claimed in  claim 2 , wherein the protuberance extends transversely with respect to the rod. 
     
     
       4. The nacelle as claimed in  claim 3 , wherein the zone of the internal face of the shroud comprises at least one shoulder oriented inward. 
     
     
       5. The nacelle as claimed in  claim 4 , wherein the protuberance is on a path of the shoulder when the shroud is turned down in a direction of an operating position while the control handle is not located in the locking position and/or the blocking member is not in the blocking position. 
     
     
       6. The nacelle as claimed in  claim 5 , wherein the shoulder comprises a part of a stiffener equipping the internal face of the shroud. 
     
     
       7. An aircraft, comprising at least one nacelle as claimed in  claim 1 .